GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 456 AIRFOIL (goe456-il) Reynolds number: 100,000 Max Cl/Cd: 64.58 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe456-il-100000-n5.txt Download as CSV file: xf-goe456-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 456 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3090 0.11325 0.10865 -0.0381 1.0000 0.0321
-8.500 -0.3138 0.11153 0.10701 -0.0372 1.0000 0.0322
-8.250 -0.3204 0.11003 0.10560 -0.0359 1.0000 0.0322
-7.750 -0.3182 0.10287 0.09856 -0.0314 1.0000 0.0332
-7.500 -0.3209 0.10061 0.09636 -0.0289 1.0000 0.0339
-7.250 -0.3237 0.09859 0.09439 -0.0276 0.9991 0.0346
-7.000 -0.3073 0.09487 0.09067 -0.0317 0.9931 0.0358
-6.750 -0.2906 0.09109 0.08689 -0.0366 0.9863 0.0370
-6.500 -0.2693 0.08690 0.08270 -0.0432 0.9789 0.0389
-6.250 -0.2354 0.08281 0.07858 -0.0592 0.9683 0.0418
-6.000 -0.2082 0.07842 0.07413 -0.0678 0.9597 0.0421
-5.750 -0.2033 0.07400 0.06975 -0.0624 0.9570 0.0451
-5.500 -0.1824 0.07042 0.06613 -0.0662 0.9495 0.0478
-5.250 -0.1262 0.06436 0.05986 -0.0863 0.9423 0.0551
-4.750 -0.0842 0.05398 0.04936 -0.0894 0.9303 0.0285
-4.250 -0.0025 0.04037 0.03514 -0.1051 0.9182 0.0212
-4.000 0.0386 0.03473 0.02905 -0.1112 0.9148 0.0205
-3.750 0.0681 0.03051 0.02427 -0.1135 0.9067 0.0202
-3.500 0.1060 0.02665 0.01967 -0.1164 0.9026 0.0202
-3.250 0.1375 0.02431 0.01667 -0.1171 0.8962 0.0212
-3.000 0.1700 0.02205 0.01390 -0.1182 0.8906 0.0235
-2.750 0.2060 0.02027 0.01177 -0.1196 0.8869 0.0252
-2.500 0.2324 0.01916 0.01043 -0.1190 0.8783 0.0276
-2.250 0.2670 0.01807 0.00911 -0.1200 0.8738 0.0346
-2.000 0.2941 0.01732 0.00814 -0.1196 0.8652 0.0423
-1.750 0.3280 0.01612 0.00729 -0.1207 0.8602 0.1381
-1.500 0.3547 0.01614 0.00736 -0.1205 0.8510 0.2234
-1.250 0.3861 0.01591 0.00699 -0.1211 0.8448 0.2502
-1.000 0.4134 0.01570 0.00667 -0.1208 0.8360 0.2643
-0.750 0.4429 0.01549 0.00637 -0.1209 0.8282 0.2840
-0.500 0.4731 0.01525 0.00608 -0.1213 0.8205 0.3107
-0.250 0.5006 0.01503 0.00590 -0.1212 0.8115 0.3525
0.000 0.5303 0.01438 0.00571 -0.1215 0.8048 0.5031
0.500 0.5933 0.01358 0.00543 -0.1225 0.7875 1.0000
0.750 0.6208 0.01366 0.00537 -0.1223 0.7785 1.0000
1.000 0.6473 0.01378 0.00539 -0.1220 0.7691 1.0000
1.250 0.6766 0.01383 0.00533 -0.1221 0.7617 1.0000
1.500 0.7019 0.01400 0.00544 -0.1216 0.7517 1.0000
1.750 0.7288 0.01412 0.00551 -0.1214 0.7432 1.0000
2.000 0.7563 0.01424 0.00560 -0.1212 0.7350 1.0000
2.250 0.7819 0.01439 0.00575 -0.1208 0.7248 1.0000
2.500 0.8083 0.01450 0.00583 -0.1203 0.7140 1.0000
2.750 0.8345 0.01458 0.00588 -0.1198 0.7015 1.0000
3.000 0.8602 0.01466 0.00600 -0.1191 0.6876 1.0000
3.250 0.8854 0.01477 0.00610 -0.1183 0.6725 1.0000
3.500 0.9103 0.01490 0.00625 -0.1175 0.6572 1.0000
3.750 0.9355 0.01506 0.00649 -0.1168 0.6432 1.0000
4.000 0.9611 0.01526 0.00677 -0.1163 0.6319 1.0000
4.250 0.9864 0.01548 0.00710 -0.1157 0.6205 1.0000
4.500 1.0098 0.01570 0.00742 -0.1146 0.6024 1.0000
4.750 1.0269 0.01590 0.00754 -0.1120 0.5547 1.0000
5.000 1.0397 0.01633 0.00768 -0.1087 0.4771 1.0000
5.250 1.0414 0.01783 0.00815 -0.1040 0.3100 1.0000
5.500 1.0422 0.02009 0.00943 -0.1001 0.1751 1.0000
5.750 1.0406 0.02267 0.01105 -0.0959 0.0302 1.0000
6.000 1.0558 0.02375 0.01227 -0.0937 0.0232 1.0000
6.250 1.0697 0.02498 0.01372 -0.0913 0.0206 1.0000
6.500 1.0840 0.02615 0.01519 -0.0890 0.0194 1.0000
6.750 1.0972 0.02734 0.01660 -0.0867 0.0177 1.0000
7.000 1.1071 0.02860 0.01806 -0.0840 0.0160 1.0000
7.250 1.1135 0.03006 0.01970 -0.0808 0.0153 1.0000
7.500 1.1188 0.03163 0.02141 -0.0776 0.0149 1.0000
7.750 1.1240 0.03338 0.02327 -0.0746 0.0145 1.0000
8.000 1.1329 0.03524 0.02520 -0.0721 0.0143 1.0000
8.250 1.1505 0.03730 0.02728 -0.0706 0.0140 1.0000
8.750 1.2240 0.04420 0.03438 -0.0730 0.0118 1.0000
9.000 1.2495 0.04728 0.03783 -0.0726 0.0118 1.0000
9.250 1.2699 0.05092 0.04179 -0.0717 0.0119 1.0000
9.500 1.2891 0.05582 0.04699 -0.0710 0.0122 1.0000
10.250 1.3004 0.06184 0.05402 -0.0619 0.0133 1.0000
10.500 1.2889 0.06383 0.05644 -0.0573 0.0139 1.0000
10.750 1.2761 0.06664 0.05965 -0.0535 0.0145 1.0000
11.000 1.2639 0.07000 0.06336 -0.0507 0.0151 1.0000
11.250 1.2503 0.07382 0.06749 -0.0487 0.0156 1.0000
11.500 1.2357 0.07786 0.07180 -0.0473 0.0161 1.0000
11.750 1.2197 0.08227 0.07645 -0.0467 0.0164 1.0000
12.000 1.2027 0.08699 0.08140 -0.0468 0.0167 1.0000
12.250 1.1848 0.09215 0.08678 -0.0478 0.0169 1.0000
12.500 1.1667 0.09768 0.09251 -0.0495 0.0170 1.0000
12.750 1.1484 0.10370 0.09872 -0.0521 0.0171 1.0000
13.000 1.1300 0.11024 0.10542 -0.0556 0.0171 1.0000
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Polar data table (+)
Polar graphs
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